[Federal Register Volume 77, Number 100 (Wednesday, May 23, 2012)]
[Rules and Regulations]
[Pages 30371-30376]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-12329]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1100; Directorate Identifier 2009-NE-37-AD; 
Amendment 39-17044; AD 2012-09-09]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all International Aero Engines AG (IAE) V2500-A1, V2525-D5 and 
V2528-D5 turbofan engines, and certain serial numbers (S/Ns) of IAE 
V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and 
V2533-A5 turbofan engines. That AD currently requires initial and 
repetitive ultrasonic inspections (USIs) of certain high-pressure 
compressor (HPC) stage 3 to 8 drums, and replacement of drum attachment 
nuts. This new AD expands the affected population for initial and 
repetitive inspections of the HPC stage 3 to 8 drum, introduces an eddy 
current inspection (ECI) procedure, and requires additional cleaning 
and repetitive USI of some HPC stage 3 to 8 drums. We are issuing this 
AD to prevent uncontained failure of the HPC stage 3 to 8 drum, which 
could result in damage to the airplane.

DATES: This AD is effective June 27, 2012.
    The Director of the Federal Register approved the incorporation by 
reference (IBR) of certain publications listed in the AD as of June 27, 
2012.

ADDRESSES: For service information identified in this AD, contact 
International Aero Engines AG, 628 Hebron Avenue, Suite 400, 
Glastonbury, CT 06033; phone: 860-368-3700; fax: 860-368-4600; email:

[[Page 30372]]

[email protected]; Web site: https://www.iaeworld.com. You may 
review copies of the referenced service information at the FAA, Engine 
& Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803. For information on the availability of this material at the FAA, 
call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Carlos Fernandes, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7189; 
fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2010-20-07, Amendment 39-16441 (75 FR 59067, 
September 27, 2010). That AD applies to the specified products. The 
NPRM published in the Federal Register on December 30, 2011 (76 FR 
82202). That NPRM proposed to continue to require initial and 
repetitive USIs of certain HPC stage 3 to 8 drums, and replacement of 
drum attachment nuts. That NPRM also proposed to expand the affected 
population for initial and repetitive inspections of the HPC stage 3 to 
8 drum, introduce an ECI procedure, and require additional cleaning and 
repetitive USI of some HPC stage 3 to 8 drums.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Request To Include Entire V2500 Fleet of Engines, and Modify the 
Optional Terminating Action

    Airbus and IAE requested that we change the applicability to 
include the entire V2500 fleet of engines, and to modify the optional 
terminating action to include partially silver plated nuts, part number 
(P/N) AS64367. The commenters stated that one new HPC stage 3 to 8 drum 
was discovered installed with partially silver plated nuts, P/N 
AS64367, that had some corrosion pitting.
    We partially agree. We agree with making a change to the optional 
terminating action, because the corrosion pitting found was on the 
optional terminating action configuration. We changed the AD, deleting 
the optional terminating action from the AD. We do not agree with 
including the entire V2500 fleet of engines, because we do not yet have 
enough information to determine what actions are needed if the nuts are 
only partially silver plated. We did not change the AD to affect the 
entire V2500 engine population.

Request To Correct Paragraph Reference Errors

    Seven commenters requested that in paragraph (i), Optional 
Terminating Action, we correct the paragraph references of (h)(1) and 
(h)(2) to (i)(1) and (i)(2).
    We agree. However, we have deleted the Optional Terminating Action 
paragraph from the AD, as described previously, and redesignated the 
subsequent paragraphs accordingly. We did not change the AD based on 
this comment.

Request To Add a Section to Previous Credit

    Air New Zealand requested that we add a section to paragraph (k), 
Previous Credit, for prior installation of a zero-time HPC stage 3 to 8 
drum that has never operated with fully silver plated nuts.
    We do not agree. We already state in Compliance paragraph (e) that 
actions are required unless the actions have already been done. We did 
not change the AD.

Request To Reference the AD Being Superseded

    Onur Air requested that we reference the AD being superseded, as it 
is not mentioned in the proposed AD.
    We do not agree. We already reference the superseded AD in the 
Discussion and in paragraph (b). We did not change the AD.

Exclude Certain HPC Stage 3 to 8 Drums

    Onur Air stated that drums which were cleaned, fluorescent 
penetrant inspected (FPI), and installed with non-fully silver plated 
nuts into the engine in a previous shop visit are not addressed, and 
should be excluded in the mandatory terminating action of the proposed 
AD.
    We do not agree. These drums are subject to the repetitive 
inspections specified in the AD. We did not change the AD.

Request To Rewrite Paragraphs (f) and (h)

    Christchurch Engine Centre and United Airlines requested that we 
rewrite paragraph (f) and (h) because they believe those paragraphs 
imply that the grace period of FPI or ECI apply to the repetitive USI 
frequency.
    We do not agree. The grace period affects the USI start, based on 
the type of previous inspection and not the USI re-inspection interval. 
As specified in paragraph (h) of the proposed AD, USI inspections are 
to be done every 750 cycles-since-last USI. If an FPI is done, then the 
USI is required within 2,500 cycles from the FPI, and then done every 
750 cycles-since-last USI. The process for the ECI is the same. We did 
not change the AD.

Request To Use the Engine Manual (EM) Instead of the Service Bulletin 
(SB) for Cleaning

    Christchurch Engine Centre and IAE requested that cleaning be done 
using the EM instead of the SB.
    We partially agree. The EM or the SB may be used as the cleaning 
procedure. We changed the AD to include the EM and SB as guidance for 
the cleaning procedure.

Request To Correct a Service Bulletin No.

    Christchurch Engine Centre requested that we correct an error in 
the SB No. in paragraph (k)(4) of the proposed AD from ``V2500-ENG-72-
615'' to ``V2500-ENG-72-0615''.
    We agree. We changed the AD to use the correct SB No. V2500-ENG-72-
0615.

Request To Incorporate by Reference (IBR) SBs

    Christchurch Engine Centre requested that we IBR the SBs into the 
AD, and stated that the proposed AD is missing the Material 
Incorporated by Reference section.
    We agree. In the NPRM, we identified SBs needed for compliance. But 
in NPRMs, we do not set them in a separate IBR paragraph. In our final 
rules we do, as required by the Office of the Federal Register. In this 
final rule, we IBR'd SBs necessary for compliance in the AD.

[[Page 30373]]

Request To Reconsider the Cost of Compliance

    Japan Airlines requested that we reconsider the Cost of Compliance. 
Based on their experience, they believe it requires at least 11 hours 
to perform the required work.
    We do not agree. The hours are based on average times provided by 
the type certificate holder. Actual times may vary depending on engine 
configuration and number of engines inspected. We did not change the 
Cost of Compliance.

Request To Mandate Only Relevant Sections of the USI Procedures

    Japan Airlines and United Airlines requested that the AD mandate 
only the relevant sections of the USI procedures in IAE Non-
Modification SB (NMSB) No. V2500-ENG-72-0608, Revision 3, dated 
September 20, 2011, and NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011.
    We agree. We changed the AD to clarify the initial inspection 
requirements of the AD.

Request for Previous Credit

    Japan Airlines and United Airlines requested that we give previous 
credit for operators using earlier revisions of the USI SBs listed in 
the proposed AD, as some operators have already inspected using the 
earlier revisions.
    We agree. We changed AD to give credit for commpliance to the 
earlier SBs listed in the AD.

Request To Allow Special Flight Permits

    United Airlines and TAM Airlines requested that we allow Special 
Flight Permits so that the airplane can be flown to a location where 
the work required by the AD can be performed.
    We do not agree. The AD already allows flights to a repair 
facility. We did not change the AD.

Request To Include All HPC Stage 3 to 8 Drum P/N Possibilities

    United Airlines requested that we include all HPC stage 3 to 8 drum 
P/N possibilities in the SB. The commenter believes that drum P/N 
6B1404, which is manufactured from the same titanium material as drum 
P/N 6A8316, should be included.
    We do not agree. The AD currently applies to all engines with HPC 
stage 3 to 8 drums that operated with fully silver plated nuts. Drum P/
N 6B1404 was introduced into production with engine S/N higher than 
V13191 and ``Select One'' engines S/N higher than V15575, and are 
outside of the applicability of this AD. We did not change the AD.

Request To Clarify Piece-Part Exposure Definition

    United Airlines and MTU Maintenance Hanover GmbH requested that we 
clarify the definition of piece-part exposure.
    We agree. We changed the definition to: ``For the purpose of this 
AD, piece-part exposure is removal of the HPC stage 3 to 8 drum from 
the engine, removal of all blades from the drum, and separation of the 
HPC stage 3 to 8 drum from the stage 9 to 12 drum.''

Request To Remove Redundant SB Listing

    IAE requested that we remove the redundant listing of NMSB No. 
V2500-ENG-72-0615, Revision 3, dated September 20, 2011, under Relevant 
Service Information in the preamble of the proposed AD.
    We agree. However, we do not repeat the Relevant Service 
Information in the final rule. We did not change the AD.

Request To Clarify Compliance Timeframe and Establish a Calendar End-
Date

    IAE requested that we clarify why a compliance timeframe is 
required to remove all fully silver plated nuts and also establish a 
calendar end-date of 2021.
    We do not agree. The unsafe condition results from a corrosive 
operating environment. The amount of corrosion varies with time and 
location, and we have no data to support a calendar end-date of 2021. 
We did not change the AD.

Request To Delay USI Start Time and Repeat Inspection Time

    TAM Airlines requested that we delay the USI start time to 13,500 
cycles-since-new, and increase the repeat inspection time to 1,500 
cycles-since-the-last USI.
    We do not agree. The initial and repetitive inspection intervals 
were established based on field experience, and extensive analysis and 
testing. We have no data that supports an increase in the compliance 
times. We did not change the AD.

Request for Special Increase Limit

    PT GMF Aeroasia requested that we allow them a special increase 
limit for one of their engines that is above 13,700 cycles to allow 
time to receive the special tooling required for the inspections.
    We do not agree. The analysis and testing does not support 
continued safe flight above 13,700 cycles. We did not change the AD.

Request for Changes To Make It Easier for Operators to Comply With the 
AD

    United Airlines requested that we add specific accept/reject 
criteria of missing liner material in the USI inspection area. The 
commenter also requested that we remove the requirement for borescoping 
the HPC stage 7 to 8 drum ceramic liner for staining or axial cracking, 
or, that we specify accept/reject criteria for staining and cracking of 
the ceramic liner. They also requested that we delay blending limit 
measurements of the HPC case port and add details for material removal 
to allow access for the probe manipulators. These changes would make it 
easier for operators to comply with the AD and avoid unnecessary 
delays.
    We partially agree. We agree with specifying accept/reject criteria 
for missing liner material in the USI inspection area. The borescope 
requirement of the HPC stage 7 to 8 drum ceramic liner for staining or 
axial cracking improves the probability of detection, however we agree 
to remove it due to lack of clear accept/reject criteria. We do not 
agree with including in the AD when to perform blending limits 
measurements and adding details for material removal to allow access 
for the probe manipulators because they are part of preparation. We 
added to the AD that any liner loss which results in lifting of the USI 
probe from the liner will need to be repaired to perform an acceptable 
inspection. Liner loss found under the intended path of the USI probe 
must be smaller than the head of the probe.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We also determined that 
these changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect about 906 IAE V2500-A1, V2522-
A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, 
V2530-A5, and V2533-A5 turbofan engines installed on airplanes of U.S. 
registry. We estimate that it will take about 3 work-hours per engine 
to perform the USI, and about 2 work-hours per engine to perform the 
FPI of the HPC stage 3 to 8 drum. The average labor rate is $85 per 
work-hour. We also estimate that removal of silver residue from the 
engine will cost about $2,600

[[Page 30374]]

per engine, and required parts about $795 per engine. We also estimate 
the cost of replacing a drum if found cracked will be $189,000. We have 
no way of determining the number of aircraft that might need this 
replacement. Based on these figures, we estimate the total cost of the 
AD to U.S. operators to be $4,385,040.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2010-20-07, Amendment 39-16441 (75 FR 59067, September 27, 2010), and 
adding the following new AD:

2012-09-09 International Aero Engines AG: Amendment 39-17044; Docket 
No. FAA-2009-1100, Directorate Identifier 2009-NE-37-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective June 27, 2012.

(b) Affected ADs

    This AD supersedes AD 2010-20-07, Amendment 39-16441 (75 FR 
59067, September 27, 2010).

(c) Applicability

    This AD applies to:
    (1) All International Aero Engines AG (IAE) V2500-A1 turbofan 
engines; and
    (2) All IAE V2525-D5 and V2528-D5 turbofan engines; and
    (3) IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, 
V2530-A5, and V2533-A5 turbofan engines with serial numbers (S/Ns) 
up to and including V13181, and with S/Ns from V15000 up to and 
including V15245.

(d) Unsafe Condition

    This AD results from reports of 50 additional high-pressure 
compressor (HPC) stage 3 to 8 drums found cracked since AD 2010-20-
07 was issued. We are issuing this AD to prevent failure of the HPC 
stage 3 to 8 drum, uncontained engine failure, and damage to the 
airplane.

(e) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified unless the actions 
have already been done.

(f) Initial Ultrasonic Inspections (USIs) of the HPC Stage 3 to 8 
Drum--``Group A''

    For IAE V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, 
V2527M-A5, V2530-A5, and V2533-A5 turbofan engines with S/Ns in 
``Group A'' in paragraph 1.A. in IAE Non-Modification Service 
Bulletin (NMSB) No. V2500-ENG-72-0615, Revision 3, dated September 
20, 2011, perform an initial USI of the HPC stage 3 to 8 drum before 
accumulating 5,000 cycles-since-new (CSN) or within 500 cycles from 
the effective date of this AD, whichever occurs later, as follows:
    (1) For IAE V2500-A1 turbofan engines:
    (i) For on-wing inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections E, G(1) through G(5), I, and J.
    (ii) For on-wing inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections L, N(1) through N(5), P(1), and Q.
    (iii) For shop inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections AU, AW(1) through AW(5), AY, and AZ.
    (iv) For shop inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections BB, BD(1) through BD(5), BF(1), and BG.
    (v) Any liner loss which results in lifting of the USI probe 
from the liner will need to be repaired in order to perform an 
acceptable inspection. Liner loss found under the intended path of 
the USI probe must be smaller than the head of the probe.
    (2) For V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, 
V2530-A5, and V2533-A5 turbofan engines:
    (i) For on-wing inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections Z, AB(1) through AB(5), AD, and AE.
    (ii) For on-wing inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections AG, AI(1) through AI(5), AK(1), and AL.
    (iii) For shop inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections BO, BQ(1) through BQ(5), BS, and BT.
    (iv) For shop inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections BV, BX(1) through BX(5), BZ(1), and CA.
    (v) Any liner loss which results in lifting of the USI probe 
from the liner will need to be repaired in order to perform an 
acceptable inspection. Liner loss found under the intended path of 
the USI probe must be smaller than the head of the probe.

(g) Initial USIs of the HPC Stage 3 to 8 Drum--``Group B''

    For IAE V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, 
V2527M-A5, V2530-A5, and V2533-A5 Turbofan Engines with S/Ns in 
``Group B'' in Paragraph 1.A. in IAE NMSB No. V2500-ENG-72-0615, 
Revision 3, dated September 20, 2011, perform an initial USI of the 
HPC stage 3 to 8 drum before accumulating 12,500 CSN or within 500 
cycles from the effective date of this AD, whichever occurs later, 
not to exceed 13,700 CSN, as follows:
    (1) For IAE V2500-A1 turbofan engines:

[[Page 30375]]

    (i) For on-wing inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections E, G(1) through G(5), I, and J.
    (ii) For on-wing inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections L, N(1) through N(5), P(1), and Q.
    (iii) For shop inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections AU, AW(1) through AW(5), AY, and AZ.
    (iv) For shop inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections BB, BD(1) through BD(5), BF(1), and BG.
    (v) Any liner loss which results in lifting of the USI probe 
from the liner will need to be repaired in order to perform an 
acceptable inspection. Liner loss found under the intended path of 
the USI probe must be smaller than the head of the probe.
    (2) For V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, 
V2530-A5, and V2533-A5 turbofan engines:
    (i) For on-wing inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections Z, AB(1) through AB(5), AD, and AE.
    (ii) For on-wing inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections AG, AI(1) through AI(5), AK(1), and AL.
    (iii) For shop inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections BO, BQ(1) through BQ(5), BS, and BT.
    (iv) For shop inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0615, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections BV, BX(1) through BX(5), BZ(1), and CA.
    (v) Any liner loss which results in lifting of the USI probe 
from the liner will need to be repaired in order to perform an 
acceptable inspection. Liner loss found under the intended path of 
the USI probe must be smaller than the head of the probe.

(h) Initial USIs for All IAE V2525-D5 and V2528-D5 Turbofan Engines

    (1) For all IAE V2525-D5 and V2528-D5 turbofan engines, perform 
an initial USI of the HPC stage 3 to 8 drum before accumulating 
12,500 CSN or within 500 cycles from the effective date of this AD, 
whichever occurs later, not to exceed 13,700 CSN.
    (i) For on-wing inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0608, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections E, G(1) through G(5), I, and J.
    (ii) For on-wing inspections of the inner diameter, perform an 
initial USI using IAENMSB No. V2500-ENG-72-0608, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections L, N(1) through N(5), P(1), and Q.
    (iii) For shop inspections of the outer diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0608, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections Z, AB(1) through AB(5), AD, and AE.
    (iv) For shop inspections of the inner diameter, perform an 
initial USI using IAE NMSB No. V2500-ENG-72-0608, Revision 3, dated 
September 20, 2011, Accomplishment Instructions, paragraph 3, 
sections AG, AI(1) through AI(5), AK(1), and AL.
    (v) Any liner loss which results in lifting of the USI probe 
from the liner will need to be repaired in order to perform an 
acceptable inspection. Liner loss found under the intended path of 
the USI probe must be smaller than the head of the probe.

(i) Removal of All Fully Silver Plated Nuts

    (1) At the next piece part exposure of the HPC stage 3 to 8 drum 
after the effective date of this AD, but no later than 8 years from 
the effective date of this AD, do the following before returning any 
HPC stage 3 to 8 drum to service:
    (i) Remove from service all fully silver plated nuts, part 
number AS44862 or equivalent that attach the HPC stage 3 to 8 drum 
to the HPC stage 9 to 12 drum.
    (ii) Remove the silver residue from the HPC stage 3 to 8 drum. 
You can find guidance to remove the silver residue of the HPC stage 
3 to 8 drum in IAE NMSB No. V2500-ENG-72-0601, Revision 2, dated 
April 12, 2010, or in IAE engine manual task 72-41-11-110-001.
    (2) Perform an inspection using one of the following methods:
    (i) Fluorescent penetrant inspect (FPI) the HPC stage 3 to 8 
drum for cracks, and remove from service any drum found cracked. You 
can find guidance on performing an FPI of the HPC stage 3 to 8 drum 
in IAE engine manual task 72-41-11-200-001.
    (ii) Eddy current inspect (ECI) the HPC stage 3 to 8 drum for 
cracks, using IAE NMSB No. V2500-ENG-72-0625, dated September 20, 
2011, and remove from service any drum found cracked.
    (3) If cracks or crack indications are identified, remove the 
drum from service before further flight.
    (4) Accomplishing paragraphs (i)(1) and (i)(2) of this AD before 
the inspection criteria requirements of paragraphs (f), (g) or (h) 
of this AD, may be substituted for the initial USI requirement of 
paragraphs (f), (g) or (h) of this AD.

(j) Repetitive USIs of the HPC Stage 3 to 8 Drum

    Perform repetitive USIs of the HPC stage 3 to 8 drum for cracks 
in accordance with paragraphs (f)(1), (f)(2), (g)(1), (g)(2), or 
(h)(1) of this AD as applicable, as follows:
    (1) Within every 750 cycles-since-last USI; or
    (2) Within 2,500 cycles-since-last FPI; or
    (3) Within 13,000 cycles-since-last ECI, whichever occurs 
latest.

(k) Definition

    For the purpose of this AD, piece-part exposure is removal of 
the HPC stage 3 to 8 drum from the engine, removal of all blades 
from the drum, and separation of the HPC stage 3 to 8 drum from the 
stage 9 to 12 drum.

(l) Credit for Previous Actions

    (1) If you performed a USI before the effective date of this AD 
using the following IAE NMSB's, you met the requirements of this AD:
    (i) IAE NMSB No. V2500-ENG-72-0594, Revision 3, dated August 7, 
2009, or Revision 4, dated October 13, 2009; or Revision 5, dated 
November 23, 2009; or Revision 6, dated April 12, 2010.
    (ii) IAE NMSB No. V2500-ENG-72-0603, Initial Issue, dated 
November 24 2009; or Revision 1, dated December 18, 2009; or 
Revision 2, dated March 17, 2010.
    (iii) IAE NMSB No. V2500-ENG-72-0608, Initial Issue, dated May 
5, 2010; Revision 1, dated August 6, 2010; or Revision 2, dated 
January 4, 2011.
    (iv) IAE NMSB No. V2500-ENG-72-0615, Initial Issue, dated July 
19, 2010; Revision 1, dated August 2, 2010; or Revision 2, dated 
November 24, 2010.

(m) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve AMOCs for 
this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(n) Related Information

    (1) For more information about this AD, contact Carlos 
Fernandes, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7189; fax: 781-238-7199; email: 
[email protected].
    (2) Guidance on removing the silver residue of the HPC stage 3 
to 8 drum may be found in International Aero Engines Service 
Bulletin No. V2500-ENG-72-0601, Revision 2, dated April 12, 2010, 
and in IAE engine manual task 72-41-11-110-001.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (i) International Aero Engines Non-Modification Service Bulletin 
No. V2500-ENG-72-0608, Revision 3, dated September 20, 2011.
    (ii) International Aero Engines Non-Modification Service 
Bulletin No. V2500-ENG-72-0615, Revision 3, dated September 20, 
2011.
    (iii) International Aero Engines Non-Modification Service 
Bulletin No. V2500-ENG-72-0625, dated September 20, 2011.

[[Page 30376]]

    (3) For service information identified in this AD, contact 
International Aero Engines AG, 628 Hebron Avenue, Suite 400, 
Glastonbury, CT 06033; phone: 860-368-3700; fax: 860-368-4600; 
email: [email protected]; Web site: https://www.iaeworld.com.
    (4) You may review copies of the service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA. For information on the availability of this material 
at the FAA, call 781-238-7125.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr_locations.html.

    Issued in Burlington, Massachusetts, on May 2, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-12329 Filed 5-22-12; 8:45 am]
BILLING CODE 4910-13-P